Gas turbine power plant



Aug. 13, 1935. SAMUELSQN 2,011,420

GAS TURBINE POWER PLANT Filed June 14. 1;)33 2 Sheets-Sheet 1 Invent OT:

Fhedrick Samuelson.

His Att oPn e q.

Aug. 13, 1935. F, AMUEL ON 2,011,420

GAS TURBINE POWER PLANT Filed June 14, 1933 2 Sheets-Sheet 2 His Aob obn e g.

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[K m 101 ms Inventor: \J- Fhedehick Samuelson.

Patented Aug. 13, 1935 UNITED STATES PATENT OFFICE GAS TURBINE POWER rum New York Application June 14. 1933, Serial No. 675,778

Great Britain January 0. 1988 ilClaims.

The present invention relates to gas turbine powers plants in which air is supplied to a rurnace and the furnace gases are mixed with additional air and the mixture conducted to a high pressure turbine.

One object of my invention is to provide an im proved construction and arrangement of such power plants in which the gases exhausted from a high pressure turbine are conducted to a low pressure turbine whereby the condition oi the gases supplied to the last named turbine may be eflectively controlled and the total emciency of the plant thereby substantially improved.

For a consideration of what I believe to be novel 1 and my invention, attention is directed to the following description and the claims appended thereto in connection with the accompanying drawings.

In the drawings, Fig. 1 represents a diagrammatic illustration oi a power plant embodying my invention; Fig. 2 shows a modification of a pert of Fig. 1; and Figs. 3 and 4 illustrate modifications of a power plant in accordance with my invention.

The arrangement shown in Fig. 1 comprises a furnace l having an inner wall I! of cylindrical shape defining a combustion chamber or space ll. A Jacket or outer wall It is concentrically arranged with the inner wall ii to define an annular space It communicating at the right-hand end through an opening or openings It with the combustion space. Combustible material is supplied to the combustion space by a burner ll pro-- jetting through a hole II in the bottom portion oi the cylindrical member l2. Air for maintaining the combustion in the combustion space is conducted through a conduit is including a valve 20 for controlling the flow 01' air through the annular opening defined by hole It and the burner II. A conduit 2| connected to the jacket ll serves to conduct air into the space II. The fiow of air to this space is controlled by a valve 22 in the conduit II.

Dm'ing operation a portion of the combustion gasesfiowsthroughtheopenings iiandismixed withtheairinthe space ll,themixturebeing conducted throu h a conduit II to the inlet of a high pressure turbine 24. To secure a thorough mixing of the combustion gases and the air in the space it I provide baiiie plates 23 near the right-hand end of the space II.

The high pressure turbine 24 has been shown in the present instance as driving an alternator 28 connected to an electric line 21. An exciter I.

i'or the alternator is coupled with the latter.

Connected to the exhaust oi the gas turbine 24 is one end of a cross-over conduit 29 which has its other end connected to the inlet of another turbine 30. This arrangement permits the conversion of available energy oi the exhaust gases s into mechanical energy by the low pressure turbine 30. The mechanical load output of the latter is in the present instance utilized for driving a compressor or blower 3| coupled to the turbine and supplying air to the furnace Hi. The exhaust oi the turbine 30 is connected to a heat exchanger 32 comprising a plurality of tubes as through which air is conducted and discharged into the suction conduit 34 of the compressor or blower I i An important feature of my invention is the provision oi means for reheating the exhaust gases discharged from the high pressure turbine 24 to obtain the desired temperature 01' these gases in the inlet to the turbine 30. These means comprise a conduit 35 for conducting combustion gases from the combustion space I! into the cross-over conduit 29. The combustion gases are mixed within the conduit 29 with the exhaust gases of turbine 24 and the mixture is supplied to the low pressure turbine. The pressure within the combustion space I3 is higher than the exhaust pressure of turbine 24. The pressure diii'erence is utilized in accordance with my invention to accelerate the velocity of the exhaust 3 gases within the conduit is. This is accomplished by the provision 01' a nozzle 36 at the end of the conduit ll, which nozzle discharges in the direction of flow of the exhaust. The higher pressure of the combustion gases conducted through conduit 36 is partly converted into velocity energy within the nozzle 36. The velocity energy is afterwards converted into pressure energy to increase the pressure ahead of the inlet oi the low pressure turbine.

The flow of gases within the conduit 35 is controlled by a valve 31 which is regulated in response to a condition of the gases flowing into the turbine 30. In the present instance I have shown a device for operating the valve 31 in 5 response to temperature changes in the conduit 29. This device comprises a bellows 30 having its upper end connected to the valve 31 by means of a link 30. The lower end 01 the bellows is provided with a conduit ll having a sealed end portion ll projecting into the conduit 29. The sealed space defined within the conduit and the bellows contains a fluid, for instance. air. As the temperature within conduit 29 increases, the

fiuid contained in the end portion ll of the com within the conduit and the bellows increases and causes expansion of the bellows and accordingly upward movement of the upper end or the bellows, turning the valve 31 in closing direction. This is a known kind of temperature-responsive device for operating a valve in response to temperature changes. A similar arrangement is provided with respect to valve 22 in the conduit 2| to regulate the flow of air into the space IS in response to temperature changes oi the mixture of air and combustion gases. This device comprises a bellows 42 having one end connected to valve 22 and another end connected to a conduit 43 provided with a sealed end 44 projecting into the mixing chamber i5 near the conduit 23. An increase of temperature of the gas-air mixture causes fluid contained within conduit 43 and the bellows to expand, resulting in expansion of the bellows and opening movement of the valve 22. This permits an increased flow of air to the mixing space or chamber l5, resulting in a decrease in temperature of the gas-air mixture discharged into the high pressure turbine.

Fig. 2 shows a modification of the cross-over conduit for conducting gases from the high pressure to the low pressure turbine and the conduit for ejecting gases from the combustion chamber into the cross-over conduit. A cross-over conduit 5D has its lower end connected to the inlet conduit 5| of a low pressure turbine. A conduit 52 corresponding to the conduit 35 of Fig. 1 has an end projecting into the cross-over conduit 50 and provided with a nozzle defining an ejector 53 for discharging combustion gases from the combustion chamber in the direction of flow of exhaust gases within the cross-over conduit 50. Whereas I have shown in Fig. 1 a butterfly valve 31 for dampening the flow of combustion gases, I provide in accordance with the modification of Fig. 2 a needle valve 54 for regulating the discharge of combustion gases from the ejector 53. This arrangement serves for utilizing the difference in pressure between the combustion chamber and the high-pressure turbine on t. The velocity of the gases discharged from me combustion chamber into the cross-over conduit is increased by the restriction formedby the nozzle ejector 53. The high velocity of the gases is afterwards converted into pressure energy as the gases leave the nozzle 53. The low-pressure turbine will thus operate with an inlet pressure somewhat above the high-pressure turbine outlet pressure. At the same time a homogeneous temperature gas mixture is obtained ahead of the inlet of the low-pressure turbine.

The arrangement shown in Fig. 3 comprises a furnace corresponding to the furnace ID in Fig. 1 forming a combustion chamber GI and a mixing space or chamber 92, and including means for utilizing a part 01' the heat energy in the combustion chamber to produce steam or like elastic fluid. This means has been diagrammatically indicated as a container for fluid 63 along the inner surface of the combustion chamber 6| having an inlet conduit 84 for receiving liquid to be evaporated and an outlet conduit 65 for discharging the fluid heated and partly evaporated in the container 63. A gas turbine 99 has an inlet conduit 91 connected to the mixing chamber 92 for receiving a'gas-air mixture from the fur nace. The available energy or this gas-air mixture is partly transformed into mechanical energy within the turbine and the exhaust is conducted by means of a cross-over conduit 99 to the duit 48 expands, to the effect that the pressureinlet of another turbine 69 which has its exhaust conduit connected by means of another crossover conduit 10 to the inlet of a third gas turbine H. The latter discharges the exhaust gases into a cross-over conduit 12 connected to the inlet of a fourth gas turbine I3 from which the exhaust is discharged into a flue 14 through the intermediary ot a heat exchanger 15. Thus the four turbines 69, 09, II and 13 are connected in series as regards the flow of the gas-air mixture from the mixing chamber 62 therethrough. The turbines 69 and H are mechanically coupled and serve for driving an alternator I6 and an exciter H. The alternator I9 is connected to an electric line 18. Each of the gas turbines 69 and I9 is coupled with a blower or compressor 19 and 99 respectively for supplying the necessary amount of air to the furnace. In the present instance 1 have shown the two compressors or blowers as being connected in series. The discharge conduit oi compressor is connected by means 01' a conduit 8| to the inletof the compressor 19, the latter having its discharge conduit 82 connected to the furnace. The suction conduit 83 of compressor 80 is connected to the heat exchanger or air preheater l5 and receives preheated air therefrom.

In order to reheat the exhaust gases supplied from one turbine to the succeeding turbine in the above mentioned series of turbines I provide means for directly conducting combustion gases from the combustion chamber 6| into each of the cross-over conduits 68, 10 and 12. These means have been indicated in the present instance as comprising a conduit 84 having its left-hand end connected to the combustion chamber 9|. The conduit 84 projects through enlarged portions 95, 86 and 81 of the cross-over conduits 98, I0 and 12 respectively. Each of these enlarged portions has a nozzle-like restriction 88, 89 and 99 respectively. The portions of the conduit 84 within the enlarged portions of the cross-over conduits have openings 9!, 92 and 93 respectively for ejecting combustion gases into the cross-over conduits. The election of combustion gases in each of the cross-over conduits takes place in the direction oi. the flow of the exhaust gases within said conduits. The combustion gases are ejected ahead of the nonlelilre restrictions 88, 89 and 99 respectively. The flow of combustion gases through conduit 94 is controlled in response to a condition of the gas mixtures in one of the cross-over conduits. In the present instance I have provided a damper in the form of a butterfly valve 94 near the inlet of conduit 84 controlled by a temperature responsive device 95 corresponding to the temperature responsive device 38, 40 of Fig. 1 and comprising a bellows 96, and a conduit 91 connected to the bellows having a sealed end projecting into the crossover conduit 12. The upper end of the bellows is connected to the damper 94. During operation an increase in temperature within the conduit 12 causes the gases in conduit 91 and the bellows 99 to expand, effecting expansion of the bellows 99, resulting in closing movement of the damper 94. The flow of gases within conduit 84 thereby decreases, eiiecting a decrease in temperature of the mixtures within the cross-over conduits. The temperature of the gas-ainmixture supplied to the high pressure turbine 96 is controlled by a device 98, corresponding to the device 4244 of Fig. 1, for positioning a valve 99 in the inlet of the mixing chamber 92.

Whereas I have shown in Fig. 3 an arrangement comprising a plurality of separate turbines and means for conducting combustion gases from J the combustion chamber to the cross-over conduits between said turbines, which means are controlled in response to the temperature of the gases in one of the cross-over conduits, I have shown in the arrangement of Fig. 4 a single turbine provided with means for reheating the gases between successive stages of the turbine by directly supplying combustion gases from a combustion sham ber to each of the lower stages of said turbine. The arrangement comprises a furnace I30 corresponding to the furnace shown in Pig. 3 and having a combustion chamber I" and a mixing chamber I02. A gas turbine I03 has an inlet con-' duit I04 receiving a gas-air mixture from the mixing chamber I02. The turbine I03 has four successive stages I00, I00, I01 and I33. The means for reheating the gases flowing from higher stages to lower stages comprise a conduit I00 connected to the combustion chamber I3I. concentrically arranged with this conduit is an outer conduit I I0. The annular space defined between the conduits I00 and H0 is separated by webs or partitions to form annular chambers III, H2 and H3. The first of these annular chambers III receives gases from the outlet of the first turbine stage I00 through a conduit H4 and discharges gases to the inlet side of the second stage I00 through a conduit I I5 connected to the first annular chamber. The conduit I00 is provided with an opening IIB for conducting combustion gases into the inlet of the conduit I I5 ahead of a nozzle-like restriction II1 of the latter. The flow of combustion gases through opening IIO of conduit I30 is controlled by a needle valve IIO having a stem projecting through the inner and outer conduits I00 and H0. Screw-threaded to the outer end of the stem is a sleeve I I0, engaging a cam I fixed On a shaft I2I. The valve stem with the sleeve is biased in opening direction by means of a spring I22 to maintain engagement with the cam I20. This arrangement permits positioning of the valve IIO either by turning the sleeve IIO on the stem or by turning the cam I20.

The arrangements for reheating the gases between the second and third and between the third and fourth stages of the turbine are similar to the arrangement for reheating the gases between the first and the second stage. The arrangement between the second and the third stage comprises a conduit I23 'for conducting at least a part of the gases from the outlet side of the stage I00 into the annular chamber H2 and a conduit I24 for conducting gases into the inlet side of the .stage I01. Provided ,'ahead of the inlet of the conduit I24 is an opening I20 through which combustion gases are conducted from the inner conduit I00 into the conduit I24. "-I'he fiow of these gases is controlled by a valve I20 regulated by a sleeve I21 and by a cam I23. The arrangement between the third and fourth stage comprises conduits I20 and I connected to the annular chamber II3. An opening I3I of the inner conduit I00 admits the supply of combustion gases into the inlet of conduit I30. The flow of these gases is controlled by a needle valve I32 corresponding to valves III and I20. The valve I32 is positioned by a sleeve I33 and by a cam I34. The three cams I20, I23 and I34 are fixed to the shaft I2I. Turning of this shaft permits the collective and simultaneous control of the fiow of combustion gases into each of the lower stages I00, I01 and I00.

In the present instance I have shown means for automatically turning the cams, that is, positioning the valves and controlling the fiow of combustion gasesin response to temperature changes in the'conduit I33aheadoftheinletofthelast stage I03. These means comprise a temperature responsive device I33 having a bellows I33 and a conduit I31 with a sealed end projecting into 6 the conduit I33. The upper end/of the bellows I30isconnectedtoalink I33 fastenedtothe shaft I2I.

During operation an increase in temperature within conduit I30 causes expansion of a gas in i0: conduit I31 and the bellows I30, to the eiiect that the bellows expands and moves the cam shaft I2I in a direction to effect a clodng movement of the needle valves II3, I20 and I32. The flow of combustion gases from the combustion chamber IOI into each of the lower stages thereby decreases, resulting in a lower temperature in conduit I33 ahead of the last stage. The sleeves H0, I21 and I33 permit individual control of the fiow of combustion gases into each of 20 the lower stages. Preferably I adjust the valves II3, I23 and I32 by means of the sleeves IIII, I21 and I33 respectively to obtain the desired temperature to the gas mixtures in conduits I I5. I24 and I30 under normal operating conditions. The temperature conditions are thereafter maintained automatically through the positioning of the cam shaft I2I by the temperature responsive device I35.

Having described the method of operation of my invention, together with the apparatus which I now consider to represent the best embodiment thereof, I desire to have it understood that the apparatus shown is only illustrative and that the invention may be carried out by other means.

What I claim as new and desire to secure by Letters Patent of the United States is:

1. In a gas turbine power plant. the combination of a furnace comprising a combustion chamber and a mixing chamber receiving gases from 40 the combustion chamber, means for supplying air to said chambers, a plurality of gas turbines, one of said turbines having an inlet connected to the mixingcha-mber, a crossvover conduit connected to the exhaust of the last named turbine,

another of said turbines having an inlet con-' nected to said conduit for receiving exhaust from the first named turbine, and means for, conducting gases from the combustion chamber into said conduit to reheat the exhaust gases of the first named turbine.

2. In a gas turbine power plant, the combination of a furnace comprising a combustion chem-,- ber and a mixing chamber receiving gases fromthe combustion chamber, means for supplying 55 air to said chambers, a plurality of gas turbines, one of said turbines having an inlet connected to the mixing chamber, a cross-over conduit connected to the exhaust oi the last named turbine] another of said turbines having an inlet con- 00 nected to the cross-over conduit for receiving exhaust from the first named turbine, means for conducting gasesfrom the combustion chamber into said conduit to reheat the exhaust gases of the first named turbine, and means for regulating the fiow of gases into said conduit in response to a condition of the gases in the inlet of the other turbine.

3. In a gas turbine power plant, the combination of a furnace comprising a combustion chamber and a mixing chamber receiving gases from the combustion chamber, means for supplying air into said chambers, a plurality of gas turbines, one of said turbines having an inlet connected to the mixing chamber, a cross-over conduit connected to the exhaust of the last named turbine, another of said turbines having an inlet connected to said cross-over conduit for receiving exhaust from the first named turbine, and means including a second conduit for conducting gases from the combustion chamber into the cross-over conduit to reheat the exhaust gases of the first named turbine, the second conduit including an ejector for converting the pressure energy of the combustion gases flowing thcrethrough into velocity energy within the cross-over conduit.

4. In a gas turbine power plant, the combination of a furnace comprising a combustion chamber and a mixing chamber receiving gases from the combustion chamber, means for supplying air to each of said chambers, means for controlling the flow of air into the mixing chamber in response to temperature changes of the gas-air mixture, a high pressure gas turbine connected to the mixing chamber, a low pressure turbine and a cross-over conduit connected to the exhaust of the first named turbine, and means for reheating the gases conducted from the high pressure into the low pressure turbine, said means comprising a conduit having one end connected to the combustion chamber and another end provided with a restriction projecting into the cross-over conduit whereby combustion gases are conducted into the cross-over conduit and their pressure energy is converted into velocity energy to increase the gas pressure in the low pressure turbine.

5. In a gas turbine power plant, the combination of a furnace comprising a combustion chamber and a mixing chamber receiving gases from the combustion chamber, means for supplying air to each of said chambers, a plurality of turbines connected in series to the mixing chamber, a cross-over conduit between each two of consecutive turbines. and means for reheating gases flowing through the cross-over conduits comprising a supply conduit for conducting gases from the combustion chamber into the cross-over conduits.

6. In a gas turbine power plant, the combination of a furnace comprising a combustion chamber and a mixing chamber receiving gases from the combustion chamber, means for supplying air to each of said chambers, a plurality of turbincs connected in series to the mixing chamber, a cross-over conduit between each two of consecutive turbines, means for reheating gases flowing through the cross-over conduits comprising a ;upply conduit for conducting gases from the combustion chamber into the cross-over conduits, means for controlling the flow of gases through the supply conduit in response. to a gas condition in one of the cross-over conduits, and a blower forming a part of the above mentioned air supply means coupled with one of said turbines.

7. In a gas turbine power plant, the combination of a furnace comprising a combustion chamber and a mixing chamber receiving gases from the combustion chamber, means for supplying air to each of said chambers, a turbine comprising a plurality of stages connected to the mixing chamber, means for reheating the gas flowing from a higher stage into a lower stage comprising a conduit for conducting gases directly from the combustion chamber into each of said stages, and means for individually and collectively controlling the fiow of gases from the combustion chamber to the diil'erent stages.

8. In a gas turbine power plant, the combination of a furnace comprising a combustion chamber and a mixing chamber receiving gases from the combustion chamber, means for supplying compressed air to each of said chambers, a gas turbine having a plurality of stages, the first stage being connected to the mixing chamber, means for reheating the gases between consecutive stages comprising an inner conduit connected to the combustion chamber, an outer conduit concentrically arranged about the inner con duit, a plurality of webs between the conduits to define annular chambers, each chamber being connected with the outlet side of one stage and the inlet side of the following stage, and means for discharging combustion gases from the inner conduit into the outer conduit, comprising a valve for each annular chamber to control the flow of combustion gases to the lower stages of the turbine.

9. In a gas turbine power plant, the combination of a high pressure turbine, a low pressure turbine, a cross-over conduit between the exhaust of the high pressure turbine and the inlet of the low pressure turbine, means for injecting high pressure combustion gases into the cross-over conduit to reheat the exhaust gases of the high pressure turbine including a nozzle in the crossover conduit for converting pressure energy of the combustion gases into velocity energy, and means in the cross-over conduit behind the nozzle as regards the direction of flow of gases for converting velocity energy of the mixture into pressure energy.

FREDERICK SAMUEIBON. 

